def fct_mission(range, aircraft, tow, payload, altp, mach, disa):
#=======================================================================================
weights = aircraft.weights
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
Y = tow - weights.owe - payload - total_fuel
return Y
def mission_tow(aircraft, payload, range, altp, mach, disa):
"""
Mission simulation (take off weight is output)
"""
weights = aircraft.weights
def fct_mission(tow, aircraft, payload, range, altp, mach, disa):
#=======================================================================================
weights = aircraft.weights
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
Y = tow - weights.owe - payload - total_fuel
return Y
#---------------------------------------------------------------------------------------
tow_ini = weights.owe + payload + 2000
fct_arg = (aircraft, payload, range, altp, mach, disa)
output_dict = fsolve(fct_mission,
x0=tow_ini,
args=fct_arg,
full_output=True)
tow = output_dict[0][0]
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
return tow, block_fuel, block_time, total_fuel
def mission_range(aircraft, tow, payload, altp, mach, disa):
"""
Mission simulation (range is output)
"""
design_driver = aircraft.design_driver
def fct_mission(range, aircraft, tow, payload, altp, mach, disa):
#=======================================================================================
weights = aircraft.weights
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
Y = tow - weights.owe - payload - total_fuel
return Y
#---------------------------------------------------------------------------------------
range_ini = design_driver.design_range
fct_arg = (aircraft, tow, payload, altp, mach, disa)
output_dict = fsolve(fct_mission,
x0=range_ini,
args=fct_arg,
full_output=True)
range = output_dict[0][0]
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
return range, block_fuel, block_time, total_fuel
def fct_mission(range, aircraft, tow, total_fuel, altp, mach, disa):
#=======================================================================================
weights = aircraft.weights
[block_fuel, block_time, fuel] = perfo.mission(aircraft, range, tow,
altp, mach, disa)
Y = total_fuel - fuel
return Y
def mission_fuel_limited(aircraft, tow, total_fuel, altp, mach, disa):
"""
Mission fuel limited (range & payload are output)
"""
design_driver = aircraft.design_driver
weights = aircraft.weights
def fct_mission(range, aircraft, tow, total_fuel, altp, mach, disa):
#=======================================================================================
weights = aircraft.weights
[block_fuel, block_time, fuel] = perfo.mission(aircraft, range, tow,
altp, mach, disa)
Y = total_fuel - fuel
return Y
#---------------------------------------------------------------------------------------
range_ini = design_driver.design_range
fct_arg = (aircraft, tow, total_fuel, altp, mach, disa)
output_dict = fsolve(fct_mission,
x0=range_ini,
args=fct_arg,
full_output=True)
range = output_dict[0][0]
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
payload = tow - weights.owe - total_fuel
return range, payload, block_fuel, block_time
def nominal_mission(aircraft):
"""
Compute nominal mission with range as input
"""
disa = 0
altp = aircraft.design_driver.ref_cruise_altp
mach = aircraft.design_driver.cruise_mach
nei = 0
aircraft.nominal_mission.payload = aircraft.payload.nominal
aircraft.nominal_mission.range = aircraft.design_driver.design_range
aircraft.nominal_mission.tow = aircraft.weights.mtow
(MTO, MCN, MCL, MCR, FID) = aircraft.propulsion.rating_code
pamb, tamb, tstd, dtodz = earth.atmosphere(altp, disa)
lod_max, _ = craft_aero.lod_max(aircraft, pamb, tamb, mach)
sfc = propu.sfc(aircraft, pamb, tamb, mach, MCR, nei)
aircraft.high_speed.cruise_lod = lod_max
aircraft.high_speed.cruise_sfc = sfc
payload = aircraft.nominal_mission.payload
range = aircraft.nominal_mission.range
tow = aircraft.nominal_mission.tow
block_fuel, block_time, total_fuel = perfo.mission(aircraft, range, tow,
altp, mach, disa)
aircraft.nominal_mission.block_fuel = block_fuel
aircraft.nominal_mission.block_time = block_time
aircraft.nominal_mission.total_fuel = total_fuel
return
def fct_mass_mission(x_in, aircraft):
ac = aircraft
ac.weights.mtow = x_in[0] # Coupling variable
ac.weights.mlw = x_in[1] # Coupling variable
ac.weights.mzfw = x_in[2] # Coupling variable
# Mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
# Mission
#------------------------------------------------------------------------------------------------------
disa = 0
altp = ac.design_driver.ref_cruise_altp
mach = ac.design_driver.cruise_mach
ac.nominal_mission.payload = ac.payload.nominal
ac.nominal_mission.range = ac.design_driver.design_range
ac.nominal_mission.tow = ac.weights.mtow
payload = ac.nominal_mission.payload
range = ac.nominal_mission.range
tow = ac.nominal_mission.tow
block_fuel, block_time, total_fuel = perfo.mission(
ac, range, tow, altp, mach, disa)
ac.nominal_mission.block_fuel = block_fuel
ac.nominal_mission.block_time = block_time
ac.nominal_mission.total_fuel = total_fuel
required_mtow = ac.weights.owe + payload + total_fuel
y_out = np.array([x_in[0] - required_mtow, \
x_in[1] - ac.weights.mlw, \
x_in[2] - ac.weights.mzfw])
return y_out
def mission_payload(aircraft, tow, range, altp, mach, disa):
"""
Mission simulation (payload weight is output)
"""
weights = aircraft.weights
[block_fuel, block_time,
total_fuel] = perfo.mission(aircraft, range, tow, altp, mach, disa)
payload = tow - weights.owe - total_fuel
return payload, block_fuel, block_time, total_fuel
pamb, tamb, tstd, dtodz = earth.atmosphere(altp, disa)
lod_max, _ = craft_aero.lod_max(ac, pamb, tamb, mach)
sfc = propu.sfc(ac, pamb, tamb, mach, MCR, nei)
ac.high_speed.cruise_lod = lod_max
ac.high_speed.cruise_sfc = sfc
ac.nominal_mission.payload = ac.payload.nominal
ac.nominal_mission.range = ac.design_driver.design_range
ac.nominal_mission.tow = ac.weights.mtow
payload = ac.nominal_mission.payload
range = ac.nominal_mission.range
tow = ac.nominal_mission.tow
block_fuel, block_time, total_fuel = perfo.mission(ac, range, tow, altp, mach,
disa)
ac.nominal_mission.block_fuel = block_fuel
ac.nominal_mission.block_time = block_time
ac.nominal_mission.total_fuel = total_fuel
mtow_eff = ac.weights.owe + payload + total_fuel
delta_mtow = mtow_i - mtow_eff # Should be positive or zero
print("-------------------------------------------")
print("Nominal mission : done")
print("")
print('Coupling : delta_mtow = ', "%.2f" % delta_mtow, 'kg, (= 0 ?)')
# Ceilings